Evaluation of NASA Lean Premixed Hydrogen Burner
The stability characteristics of a prototype premixed, hydrogen-fueled burner were studied. The potential application is the use of hydrogen as a fuel for aircraft gas turbine operation. The burner configuration consisted of nine 6.72 mm (0.265 in) diameter channels through which the reactants entered the burner. Hydrogen was injected radially inward through two 0.906-mm (0.0357 in) diameter holes located on opposite sides of each air channel. In this way the region over which hydrogen and air were premixed was minimized to prevent potential flashback problems. All tests were carried out at atmospheric pressure. Flame stability was studied over a range of fuel-lean operating conditions since lean combustion is currently recognized as an effective approach to NOx emissions reduction. In addition to pure hydrogen and air, mixtures of hydrogen-blended methane and air were studied to evaluate the potential improvements in flame stability as hydrogen replaces methane as the primary fuel component.
- Research Organization:
- Sandia National Lab. (SNL-NM), Albuquerque, NM (United States); Sandia National Lab. (SNL-CA), Livermore, CA (United States)
- Sponsoring Organization:
- US Department of Energy (US)
- DOE Contract Number:
- AC04-94AL85000
- OSTI ID:
- 811192
- Report Number(s):
- SAND2002-8609; TRN: US200310%%192
- Resource Relation:
- Other Information: PBD: 1 Jan 2003
- Country of Publication:
- United States
- Language:
- English
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